Device for measuring at least one parameter of an aerodynamic flow of a turbine engine equipped with a vibratory damping means and turbine engine duct equipped with such a device

Abstract

A measuring device for measuring at least one parameter of an aerodynamic flow of a turbine engine. The device operates to collect parameters of the flow. A body extends along a radial axis (L). A connecting part is fastened to a first end of the body and designed to secure the measuring device to a radially outer wall of the turbine engine. A stud is inserted and mounted on a second end of the body radially opposite the first end. The stud includes at least a portion of a rubberlike material designed to come into contract with a radially inner wall of the turbine engine.

The invention claimed is: 
     
       1. A measuring device for measuring at least one parameter of an aerodynamic flow of a turbine engine, the said device comprising:
 data collectors to collect parameters of the aerodynamic flow; 
 a body extending along a radial axis (L) and carrying the data collectors; 
 a connecting part fastened to a first end of the body to secure the measuring device to a radial outer wall of the turbine engine; and 
 a stud inserted and mounted on a second end of the body radially opposite the first end; 
 wherein the said stud comprises at least a portion of a rubberlike material to come into contact with a radial inner wall of the turbine engine. 
 
     
     
       2. The measuring device according to  claim 1 , wherein the stud is to come into said contact through a flexible connection with the radial inner wall, such that the flexible connection is compressed once the flexible connection comes into contact with the radial inner wall of the turbine engine. 
     
     
       3. The measuring device according to  claim 1 , wherein the stud comprises a reinforcement part moulded in said stud and made of a harder material than the stud, a distance (e) delineated between the reinforcement part and an outer surface of the stud to come into contact with the radial inner wall. 
     
     
       4. The measuring device according to  claim 3 , wherein the stud is configured such that the flexible connection is compressed at a predetermined value ranging between 1 and 4 mm, which is less than the distance (e). 
     
     
       5. The measuring device according to  claim 1 , wherein the rubberlike material is polydimethylsiloxane. 
     
     
       6. The measuring device according to  claim 1 , wherein the stud is mounted removably on the second end of the body. 
     
     
       7. The measuring device according to  claim 6 , wherein the stud is mounted removably on the second end of the casing by gluing. 
     
     
       8. The measuring device according to  claim 1 , wherein the body comprises at least an inner longitudinal cavity that extends on a radial axis (L), said longitudinal cavity accommodating at least part of a data transmitter connected to the data collectors. 
     
     
       9. The measuring device according to  claim 1 , wherein the connecting part comprises an attachment flange to be fastened to the radial outer wall of the turbine engine and to carry the said body through an aerodynamic flow of an aerodynamic duct of the turbine engine. 
     
     
       10. A duct for the aerodynamic flow of a turbine engine, the duct being annular comprising an annular radial outer wall and an annular radial inner wall, the duct being equipped with at least one measuring device according to  claim 1 , installed radially in the aerodynamic flow, the stud being fitted in between the second end of the body and the radial inner wall, and in contact with the radial inner wall through a flexible connection. 
     
     
       11. The duct according to  claim 10 , wherein a seal is fitted between the flange of the connecting part and a boss of the radial outer wall. 
     
     
       12. A method for installing a measuring device, according to  claim 1 , in a duct of the turbine engine, the method comprising:
 mounting the stud on the second end of the body of the measuring device; 
 inserting the measuring device together with the stud into the duct of the turbine engine such that the stud comes into contact with the radial inner wall of the duct of the turbine engine; 
 providing a predetermined gap (J) in between a boss of a radial outer wall of the duct of the turbine engine and the flange; 
 inserting a seal into the predetermined gap (J); 
 tightening the flange and the boss using fasteners such that there is a predetermined crushing of the stud on the radial inner wall of the duct of the turbine engine. 
 
     
     
       13. The method according to  claim 12 , comprising machining an extra thickness of the stud if the value of the gap measured between the boss and the flange is more than the value of the predetermined gap (J).